In aircraft design, the lift formula is a fundamental equation used to calculate the lift force generated by an airfoil (such as a wing) as it moves through the air. The lift force is what enables an aircraft to overcome gravity and achieve flight.
The lift formula is typically expressed as:
Where:
- is the lift force (in Newtons, N)
- is the coefficient of lift, which depends on the shape of the airfoil and the angle of attack
- (rho) is the air density (in kilograms per cubic meter, kg/m³)
- is the reference area of the airfoil (in square meters, m²)
- is the relative velocity between the airfoil and the air (in meters per second, m/s)